CN113883221A

CN113883221A - Micro-vibration isolator

Info

Publication number: CN113883221A
Application number: CN202111340101.XA
Authority: CN
Inventors: 孔令波; 姜秀鹏; 胡宝义; 阎凯
Original assignee: Beijing MinoSpace Technology Co Ltd; Anhui Minospace Technology Co Ltd; Beijing Guoyu Xingkong Technology Co Ltd; Hainan Minospace Technology Co Ltd; Shaanxi Guoyu Space Technology Co Ltd
Current assignee: Beijing MinoSpace Technology Co Ltd; Anhui Minospace Technology Co Ltd; Beijing Guoyu Xingkong Technology Co Ltd; Hainan Minospace Technology Co Ltd; Shaanxi Guoyu Space Technology Co Ltd
Priority date: 2021-11-12
Filing date: 2021-11-12
Publication date: 2022-01-04
Anticipated expiration: 2041-11-12
Also published as: CN113883221B

Abstract

The application relates to the technical field of vibration isolation, in particular to a micro-vibration isolator for an optical remote sensing satellite. The micro-vibration isolator comprises an I-shaped shaft sleeve, a vibration attenuation component and a mounting plate; the upper end surface and the lower end surface of the I-shaped shaft sleeve are respectively provided with an annular first groove, and the surface of a central shaft of the I-shaped shaft sleeve is respectively provided with an annular second groove; an axial flexible pad is respectively arranged in the two first grooves, and a radial flexible pad is respectively arranged in the two second grooves; two ends of the central shaft are respectively sleeved with a rigid cushion, inner rings of the two rigid cushions are respectively abutted with the two radial flexible cushions, and end faces of the two rigid cushions are respectively abutted with the two axial flexible cushions; the center pin is located to the mounting panel cover, and the mounting panel presss from both sides between two rigidity pads through two mounting pads. The micro-vibration isolator can simultaneously solve the problems of large-magnitude vibration of the momentum wheel in a launching environment and small-magnitude micro-vibration in an on-orbit process.

Description

Micro-vibration isolator

Technical Field

The application relates to the technical field of vibration isolation, in particular to a micro-vibration isolator for an optical remote sensing satellite.

Background

For an optical remote sensing satellite with high resolution, the influence of the micro-vibration of the momentum wheel on the imaging quality is not negligible, and the influence is more and more serious along with the improvement of the resolution, for example, the micro-vibration generated by the normal work of the momentum wheel on the satellite is found to be larger through ground test and simulation analysis by a certain type of satellite, so that the visual axis shaking of the camera reaches 0.1 arc second, which is higher than the technical index provided in the design scheme, and the imaging quality of the camera is influenced.

Therefore, isolation of the micro-vibration generated by the momentum wheel on the optical remote sensing satellite is an urgent problem to be solved.

Content of application

The utility model aims to provide a little vibration isolator can install the use on the momentum wheel mounting point of optics remote sensing satellite or optical load mounting point to solve the problem of the little magnitude of vibration of momentum wheel when launching the big magnitude of vibration under the environment and in orbit simultaneously.

The technical scheme of the application is realized as follows:

a micro-vibration isolator comprises an I-shaped shaft sleeve, a vibration attenuation component and a mounting plate;

the I-shaped shaft sleeve comprises a central shaft, an upper end surface and a lower end surface; the upper end surface and the lower end surface are respectively provided with an annular first groove, and the surface of the central shaft close to the upper end surface and the lower end surface is respectively provided with an annular second groove;

the vibration reduction assembly comprises a radial flexible pad, an axial flexible pad, a rigid pad and a mounting pad; the first grooves are internally provided with the axial flexible pads respectively, and the second grooves are internally provided with the radial flexible pads respectively; the two rigid cushions are sleeved at two ends of the central shaft, inner rings of the two rigid cushions are respectively abutted with the two radial flexible cushions, and end faces of the two rigid cushions are respectively abutted with the two axial flexible cushions;

the mounting panel cover is located the center pin, just the mounting panel is through two the mounting pad clamp is in two between the rigidity pad.

In a preferred technical scheme of the application, the maximum compression amount a of the axial flexible cushion is not more than 50% of the thickness of the axial flexible cushion in the direction of the central axis of the axial flexible cushion;

the depth of the first groove is larger than a.

In a preferred technical scheme of the application, the maximum compression amount b of the radial flexible cushion is not more than 50% of the thickness of the radial flexible cushion in the radial direction;

the depth of the second groove is greater than b.

In a preferred embodiment of the present application, the depth of the first groove is 60% of the thickness of the axially flexible pad in the direction of the central axis thereof.

In a preferred embodiment of the present application, the depth of the second groove is 60% of the thickness of the radially flexible pad in the radial direction.

In the technical scheme that this application is preferred, the elastic modulus of rigidity pad is radial flexible pad or the elastic modulus of axial flexible pad is 8 ~ 12 times.

In a preferred embodiment of the present application, the mounting pad is a rigid Z-shaped pad having a "Z" shaped longitudinal section.

In a preferred technical scheme of the present application, the i-shaped shaft sleeve includes a T-shaped sleeve and a flat gasket, the T-shaped sleeve includes a shaft portion and an end portion, the shaft portion constitutes the central shaft, and the end portion constitutes the upper end surface; the flat gasket is sleeved on the T-shaped sleeve to form the lower end face of the I-shaped shaft sleeve.

In a preferred technical scheme of the application, the micro-vibration isolator further comprises a screw and an elastic pad; the shaft part of the T-shaped sleeve is a hollow pipe, and the thread part of the screw penetrates through the elastic pad, the T-shaped sleeve and the flat gasket and is used for being connected with an installation base.

In the technical scheme of this application preferred, radial flexible pad with polyurethane rubber is all chooseed for use to the material of axial flexible pad, silicon rubber is chooseed for use to the material of rigidity pad.

The beneficial effect of this application does:

this application scheme can solve two problems of momentum wheel vibration simultaneously, and the second is the little magnitude of vibration problem of the great deal of vibration of transmission environment on the one hand, on the other hand rail.

When the satellite is in a carrying and launching stage, large-magnitude random vibration is transmitted to the momentum wheel micro-vibration isolator through the mounting point, the axial flexible pad and the radial flexible pad reach the maximum designed compression amount and are retracted into the first groove and the second groove of the I-shaped shaft sleeve due to the large vibration magnitude, deformation does not occur any more, then the rigid pad elastically deforms, the vibration energy is dissipated due to material damping because the rigid pad is also a high-damping material, and the vibration magnitude transmitted to the momentum wheel by the satellite body is also greatly attenuated, so that the effect of isolating large-magnitude vibration is achieved. The vibration environment of the launching stage is one of the main reasons for the failure of the momentum wheel, and the isolation of the vibration of the launching environment can greatly improve the service life and the reliability of the momentum wheel.

When the satellite runs in orbit, the small-magnitude micro-vibration (or chatter) generated by the momentum wheel is transmitted to the momentum wheel micro-vibration isolator through the mounting point, because the vibration magnitude is very small, the axial flexible pad and the radial flexible pad generate elastic deformation while the rigid pad hardly deforms, the deformation of the flexible pad made of a high-damping material can dissipate micro-vibration energy, the micro-vibration magnitude transmitted to the satellite body through the momentum wheel micro-vibration isolator is greatly attenuated, and the momentum wheel micro-vibration is isolated. The chatter (micro-vibration) generated by the high-speed on-orbit running of the momentum wheel is one of the reasons for insufficient imaging quality of the high-resolution optical remote sensing satellite, and the micro-vibration of the isolated momentum wheel can greatly improve the imaging quality of the remote sensing load.

The micro-vibration isolator can be applied to a momentum wheel on an optical remote sensing satellite, and can also be popularized to other products needing micro-vibration isolation, such as a gyroscope, a space camera, a space motor and the like.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings that are required to be used in the embodiments will be briefly described below, it should be understood that the following drawings only illustrate some embodiments of the present application and therefore should not be considered as limiting the scope, and for those skilled in the art, other related drawings can be obtained from the drawings without inventive effort.

FIG. 1 is a longitudinal cross-sectional view of a micro-vibration isolator provided in an embodiment of the present application;

FIG. 2 is a front view of a micro-vibration isolator according to an embodiment of the present application;

FIG. 3 is a longitudinal cross-sectional view of the T-shaped sleeve;

FIG. 4 is a cross-sectional view of an axially compliant pad;

reference numbers in the figures:

1-T-shaped sleeve; 101-a second groove;

102-a second groove; 103-a first groove;

2-flat gasket; 3-a rigid pad;

4-a mounting mat; 5, mounting a plate;

6-axially compliant pad; 7-a radially flexible mat;

8-a screw; 9-elastic cushion;

10-mounting a base.

Detailed Description

In order to make the objects, technical solutions and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application, and it is obvious that the described embodiments are some embodiments of the present application, but not all embodiments. The components of the embodiments of the present application, generally described and illustrated in the figures herein, can be arranged and designed in a wide variety of different configurations.

Thus, the following detailed description of the embodiments of the present application, presented in the accompanying drawings, is not intended to limit the scope of the claimed application, but is merely representative of selected embodiments of the application. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.

It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, it need not be further defined and explained in subsequent figures.

In the description of the present application, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings or orientations or positional relationships that the products of the application usually place when in use, and are used only for convenience in describing the present application and simplifying the description, but do not indicate or imply that the devices or elements being referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present application. Furthermore, the terms "first," "second," "third," and the like are used solely to distinguish one from another and are not to be construed as indicating or implying relative importance.

Furthermore, the terms "horizontal", "vertical", "overhang" and the like do not imply that the components are required to be absolutely horizontal or overhang, but may be slightly inclined. For example, "horizontal" merely means that the direction is more horizontal than "vertical" and does not mean that the structure must be perfectly horizontal, but may be slightly inclined.

In the description of the present application, it is further noted that, unless expressly stated or limited otherwise, the terms "disposed," "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present application can be understood in a specific case by those of ordinary skill in the art.

Some embodiments of the present application will be described in detail below with reference to the accompanying drawings. The embodiments described below and the features of the embodiments can be combined with each other without conflict.

As shown in fig. 1 and 2, the present embodiment provides a micro-vibration isolator, which includes an i-shaped bushing, a vibration damping assembly and a mounting plate 5.

Specifically, the I-shaped shaft sleeve comprises a T-shaped sleeve 1 and a flat gasket 2, the T-shaped sleeve comprises a cylindrical shaft part and a disc-shaped end part, the shaft part forms a central shaft of the I-shaped shaft sleeve, and the end part forms the upper end face of the I-shaped shaft sleeve; the flat gasket 2 is sleeved on the shaft part of the T-shaped sleeve 1 and is arranged opposite to the end part, so that the lower end surface of the I-shaped shaft sleeve is formed.

As shown in fig. 3, an annular first groove 103 is provided on the inner side surface of the end portion of the T-shaped sleeve 1 and the inner side surface of the flat gasket 2, respectively (the first groove 103 on the flat gasket 2 is not separately shown in fig. 3), and annular

second grooves

101 and 102 are provided on the shaft portion of the T-shaped sleeve 1 near both ends, respectively.

The vibration damping assembly comprises a radial flexible pad 7, an axial flexible pad 6, a rigid pad 3 and a mounting pad 4; an axial flexible pad 6 is respectively arranged in the two first grooves 103, and a radial flexible pad 7 is respectively arranged in the two

second grooves

101 and 102; the two rigid pads 3 are sleeved at two ends of the shaft part of the T-shaped sleeve 1, inner rings of the two rigid pads 3 are respectively abutted with the two radial flexible pads 7, and end faces of the two rigid pads 3 are respectively abutted with the two axial flexible pads 6.

The mounting plate 5 is sleeved on the shaft part of the T-shaped sleeve 1, and the mounting plate 5 is clamped between the two rigid pads 3 through the two mounting pads 4.

The micro-vibration isolator can be used for a momentum wheel on an optical remote sensing satellite to simultaneously solve the problems of large-magnitude vibration of the momentum wheel in a transmitting environment and small-magnitude micro-vibration in orbit. The specific vibration isolation principle is as follows:

when the satellite is in a carrying and launching stage, large-magnitude random vibration is transmitted to the momentum wheel micro-vibration isolator through the mounting point, due to the fact that the vibration magnitude is large, the axial flexible pad 6 and the radial flexible pad 7 reach the maximum design compression amount and are retracted into the first groove 103, the second groove 101 and the second groove 102 of the I-shaped shaft sleeve, deformation does not occur any more, then the rigid pad 3 elastically deforms, and due to the fact that the rigid pad 3 is also made of a high-damping material, vibration energy is dissipated due to material damping, the vibration magnitude transmitted to the momentum wheel by the satellite body is also greatly attenuated, and therefore the effect of isolating the large-magnitude vibration is achieved. The vibration environment of the launching stage is one of the main reasons for the failure of the momentum wheel, and the isolation of the vibration of the launching environment can greatly improve the service life and the reliability of the momentum wheel.

When the satellite runs in orbit, the small-magnitude micro-vibration (or chatter) generated by the momentum wheel is transmitted to the momentum wheel micro-vibration isolator through the mounting point, because the vibration magnitude is very small, the axial flexible pad 6 and the radial flexible pad 7 generate elastic deformation while the rigid pad 3 hardly deforms, the deformation of the flexible pad made of a high-damping material can dissipate micro-vibration energy, the micro-vibration magnitude transmitted to the satellite body through the momentum wheel micro-vibration isolator is greatly attenuated, and the momentum wheel micro-vibration is isolated. The chatter (micro-vibration) generated by the high-speed on-orbit running of the momentum wheel is one of the reasons for insufficient imaging quality of the high-resolution optical remote sensing satellite, and the micro-vibration of the isolated momentum wheel can greatly improve the imaging quality of the remote sensing load.

The mode of forming the I-shaped shaft sleeve by the T-shaped sleeve 1 and the flat gasket 2 is simple, and the installation and the disassembly are convenient. In other embodiments, other structures or features may be used to form the i-shaped sleeve.

In the preferred embodiment of this embodiment, the axial flexible cushion 6 and the radial flexible cushion 7 should be disposed as close as possible to the connection position of the central axis of the i-shaped shaft sleeve and the upper end surface/lower end surface, so that when the rigid cushion 3 is compressed and deformed, the relative position of the rigid cushion 3 and the axial flexible cushion 6 or the radial flexible cushion 7 is less shifted, and the shearing force therebetween is less.

The axial flexible pad 6, the radial flexible pad 7 and the rigid pad 3 are all required to be made of materials meeting the conditions of high wear resistance, good elasticity, high strength, high damping, high and low temperature resistance and the like. In this embodiment, the radial flexible pad 7 and the axial flexible pad 6 are made of polyurethane rubber, and the rigid pad 3 is made of silicone rubber.

Since it is required that the axial pads 6 and the radial pads 7 can be retracted into the first grooves 103, the

second grooves

101 and 102 of the i-shaped bushing when the maximum design compression is reached, when the satellite is in the launch phase, therefore:

in the solution of the present embodiment, the maximum compression a of the axially flexible pad 6 is not more than 50% of the thickness of the axially flexible pad 6 in the direction of its central axis, while the depth of the first groove 103 is greater than a. In a more preferable mode, the depth a of the first groove 103 is about 60% of the thickness of the axial flexible pad 6 in the direction of the central axis of the axial flexible pad 6, so that the axial flexible pad 6 can be completely pressed into the first groove 103, and the end face of the rigid pad 3 can be in contact with the inner side surface of the end of the T-shaped sleeve 1 and the inner side surface of the flat gasket 2.

The maximum compression b of the radially flexible pad 7 is not more than 50% of the thickness of the radially flexible pad 7 in itself, while the depth of the

second grooves

101 and 102 needs to be greater than b. In a more preferred embodiment, the depth b of the

second grooves

101 and 102 is about 60% of the thickness of the radially flexible pad 7 in the radial direction, so that the radially flexible pad 7 can be completely pressed into the

second grooves

101 and 102, and the inner surface of the rigid pad 3 can contact with the outer surface of the shaft portion of the T-shaped sleeve 1.

The rigidity of the axial flexible cushion 6, the radial flexible cushion 7 and the rigid cushion 3 needs to be designed according to the weight of the momentum wheel and the number of mounting points, generally, the elastic modulus of the rigid cushion 3 is one order of magnitude larger than that of the axial flexible cushion 6 and the radial flexible cushion 7, that is, approximately 8 to 12 times, for example, when the elastic modulus of the rigid cushion 3 is 10MPa, the elastic modulus of the axial flexible cushion 6 and the radial flexible cushion 7 can be designed to be 1 MPa.

The axially flexible pads 6 and the radially flexible pads 7 are each of a circular ring-shaped configuration, the longitudinal section of which is shown in fig. 4.

The mounting pad 4 is a Z-shaped pad having a Z-shaped longitudinal section and is made of a hard metal material.

The shaft of the T-shaped sleeve 1 is a hollow tube, and the thread part of the screw 8 can penetrate through the elastic pad 9, the shaft of the T-shaped sleeve 1 and the flat gasket 2 to connect the momentum wheel micro-vibration isolator with the mounting base 10. Other devices or devices may be mounted on the mounting plate 5.

The micro-vibration isolator is simple in structure, low in cost and remarkable in effect, and can be applied to momentum wheel vibration reduction and micro-vibration isolation of high-resolution optical remote sensing satellites, SAR satellites and the like. The micro-vibration isolation device can also be popularized to other products needing micro-vibration isolation, such as a gyroscope, a space camera, a space motor and the like.

The above description is only a preferred embodiment of the present application and is not intended to limit the present application, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, improvement and the like made within the spirit and principle of the present application shall be included in the protection scope of the present application.

Claims

1. A micro-vibration isolator is characterized by comprising an I-shaped shaft sleeve, a vibration attenuation component and a mounting plate;

2. The micro-vibration isolator of claim 1 wherein the maximum compression a of the axially compliant pad is no more than 50% of the thickness of the axially compliant pad in the direction of its central axis;

the depth of the first groove is larger than a.

3. The micro-vibration isolator of claim 1 wherein the maximum compression b of the radially compliant pads is no more than 50% of the radial compliant pad thickness in its radial direction;

the depth of the second groove is greater than b.

4. The micro-vibration isolator of claim 2 wherein the depth of the first recess is 60% of the thickness of the axially compliant pad in the direction of its central axis.

5. The micro-vibrating vibration isolator of claim 3 wherein the depth of the second recess is 60% of the radial compliant pad thickness in its radial direction.

6. The micro-vibration isolator of claim 1 wherein the modulus of elasticity of the stiff pads is 8 to 12 times the modulus of elasticity of the radially compliant pads or the axially compliant pads.

7. The micro-vibration isolator of claim 1 wherein the mounting pad is a rigid Z-pad having a "Z" shape in longitudinal cross section.

8. The micro-vibration isolator of claim 1 wherein the h-shaped bushing comprises a T-shaped bushing and a flat spacer, the T-shaped bushing comprising a shaft portion and an end portion, the shaft portion defining the central axis and the end portion defining the upper end surface; the flat gasket is sleeved on the T-shaped sleeve to form the lower end face.

9. The micro-vibration isolator of claim 1 further comprising a screw and a spring washer; the shaft part of the T-shaped sleeve is a hollow pipe, and the thread part of the screw penetrates through the elastic pad, the T-shaped sleeve and the flat gasket and is used for being connected with an installation base.

10. The micro-vibration isolator of claim 1, wherein the radial compliant pads and the axial compliant pads are made of polyurethane rubber, and the rigid pads are made of silicone rubber.